preflight inspection - mrmoo preflight inspection.pdf · king air 350 developed for training...

King Air 350 Developed for Training Purposes 2A-1October 2001

Preflight InspectionTable of ContentsCockpit Flow Pattern . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-3

Power Off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-5

Power On Checks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-7

Fuel Panel Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-9

Oxygen System Check . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-10

Warning System Check . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-11

Electric Trim System Check. . . . . . . . . . . . . . . . . . . . . . . 2A-12

Autopilot and Yaw Damp Check . . . . . . . . . . . . . . . . . . . 2A-12

Anti-Ice System Check . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-14

Cockpit Preflight Continued . . . . . . . . . . . . . . . . . . . . . . . 2A-15

Cabin Preflight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-16

Airstair Door Circuitry Check . . . . . . . . . . . . . . . . . . . . . . 2A-17

Preflight Inspection Walkaround Path . . . . . . . . . . . . . 2A-18

Exterior Preflight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-19

General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-19

Left Wing Trailing Edge . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-20

Left Wing Leading Edge . . . . . . . . . . . . . . . . . . . . . . . . . 2A-23

Left Engine Nacelle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-24

Left Wing Root . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-25

Left Nose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-26

Nose Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-27

Right Nose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-28

Right Wing Root. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-29

2A-2 Developed for Training Purposes King Air 350October 2001

CAE SimuFlite

Right Engine Nacelle . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-30

Right Wing Leading Edge . . . . . . . . . . . . . . . . . . . . . . . . 2A-32

Right Wing Trailing Edge . . . . . . . . . . . . . . . . . . . . . . . . . 2A-34

Right Rear Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-35

Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-36

Left Rear Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2A-37


Preflight Inspection


CAE SimuFlite

Cockpit Flow Pattern

B3

CR

H-P

F0

01

i

COCKPIT FLOW PATTERN

(LEFT SEAT)

COCKPIT FLOW PATTERN

(RIGHT SEAT)



Power OffGPU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONNECT/ON

Control Locks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REMOVEParking Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SETRight Sidewall Circuit Breaker Panel . . . . . . . . . . . . . . .CHECKAlternate Static Air Switch . . . . . . . . . . . .GUARDED NORMALCopilot’s Right Subpanel . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Check vacuum, pneumatic, and oxygen gauges for properindications.

Copilot’s Instrument Panel . . . . . . . . . . . . . . . . . . . . . . .CHECKCheck instruments for condition and proper indications.

Copilot’s Left Subpanel Switches. . . . . . . . . . . . . . . . . . . . SETSet all switches to OFF or normal positions.

Center Pedestal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECKWorking forward, set all switches to OFF or normal posi-tions. Oxygen control handles should be pushed in. Ensureall knobs, switches, and protective covers are free fromdamage.

Alternate Gear Extension Handle . . . . . . . . . . . . . . . STOWEDThe handle should be set all the way down, flush with thefloor. If the handle was in the up position, ensure that thesystem has not been emergency extended during the previ-ous flight.

Trim Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET ZEROMake sure the trims are set to zero and indicated. Trim posi-tion should be checked during walk-around.

NOTE: Prior to entering the aircraft for Preflight Inspection, pitot cover should be removed and ground power unit (GPU)should be connected and selected ON. EXT PWR annunciator should flash intermittently for the entire time GPU is connected until EXT PWR is switched ON.


CAE SimuFlite

Power Quadrant. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

Engine controls should be set as follows: power lever atFLIGHT IDLE, prop lever at FEATHER, and condition leverat FUEL CUTOFF.

Center Instrument Panel and Glareshield . . . . . . . . . . .CHECK

Make sure all switches are set to OFF or normal position.Ensure all the controls are in good condition and are prop-erly installed. Ensure the glareshield has no cracks ordamage.

Overhead Panel. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

All switches should be set to OFF or normal. Verify that 28Vis present when EXT PWR is selected and that the batteryhas minimum of 20 volts. Check the standby compass forvalid indications and condition.EXT PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28VBATT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20V (MIN)

Pilot's Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Check all instruments and switches for indication/position,security, and freedom from damage.

Pilot’s Right Subpanel Switches . . . . . . . . . . . . . . . . . . . . SET

Set all switches to OFF and ensure that the landing gearhandle is down-and-locked.

Pilot’s Left Subpanel Switches. . . . . . . . . . . . . . . . . . . . . . SET

Set all switches to OFF or normal positions. Fuel Panel Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

Set the standby pump switches to OFF and the auxiliarytransfer switches to AUTO.

Left Sidewall Circuit Breaker Panel . . . . . . . . . . . . . CHECK IN

To set parking brake, apply pressure to the top of the rudderpedals; pull the parking brake handle and release the pres-sure applied to the rudder pedals.



Power On ChecksBattery Switch . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM OFFBattery Bus Switch. . . . . . . . . . . . . . . . . . . . . . . . . .EMER OFF

Rotate the Voltmeter Bus Select switch through each posi-tion. Verify that the voltmeter indicates zero volts on all posi-tions, except EXT PWR.

Battery Bus Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM

Rotate the Voltmeter Bus Select switch through each posi-tion. Verify that the voltmeter indicates zero volts for eachposition, except Battery Volts on BAT and EXT PWRpositions.

Battery Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

Rotate the Voltmeter Bus Select switch through eachposition.Note battery voltage on BAT and CTR positions; TPL FEDposition should read slightly less than battery voltage. Allother positions should show zero voltage, except EXT PWR.Observe L DC GEN, R DC GEN, L GEN TIE OPEN, R GENTIE OPEN, #1 AC BUS, #2 AC BUS annunciator illuminated.Landing Gear Position Lights indicate 3 green.

GEN TIES Switch . . . . . . . . . . . . . . . . . . . . . . . . MAN CLOSE

Rotate the Voltmeter Bus Select switch through eachposition.Note battery voltage on ALL bus positions except TPL FED,which should read slightly less than battery voltage. EXTPWR should still read 28V DC.Observe L DC GEN, R DC GEN, MAN TIES CLOSE, #1 ACBUS, #2 AC BUS annunciators illuminated.

External Power Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

Observe MAN TIES CLOSE annunciator extinguished. EXTPWR annunciator illuminated steady.

2A-8 Developed for Training Purposes King Air 350February 2006

CAE SimuFlite

Rotate the Voltmeter Bus Select switch through each posi-tion. Note GPU voltage on all buses, with slightly less onTPL FED.

Bus Sense Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

Observe L GEN TIE OPEN, R GEN TIE OPEN, and BATTIE OPEN annunciators illuminated.Rotate the Voltmeter Bus Select switch through each posi-tion. Note zero voltage on all positions except BAT, EXTPWR, TPL FED and Center Bus.

Bus Sense Switch . . . . . . . . . . . . . . . . . . . . . . . RESET/NORM

Observe L GEN TIE OPEN, R GEN TIE OPEN and BAT TIEOPEN annunciators extinguished.

GEN TIE Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN

Observe L GEN TIE OPEN, R GEN TIE OPEN annunciatorsilluminated.Rotate the Voltmeter Bus Select switch through each posi-tion. Note GPU voltage on CTR, BAT and slightly less onTPL FED. Zero volts on each GEN bus.

GEN TIE Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORMInverter Switches (2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

No. 1 Inverter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

No. 1 AC BUS annunciator illuminated.

No. 1 Inverter . . . . . . . . . . . . . . . . . . . . . . BUS TRANSFER

No. 1 AC BUS annunciator extinguished.

No. 1 Inverter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

No. 2 Inverter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

No. 2 AC BUS annunciator illuminated.

No. 2 Inverter . . . . . . . . . . . . . . . . . . . . . . BUS TRANSFER

No. 1 AC BUS annunciator extinguished.

No. 2 Inverter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

No. 1 and 2 AC BUS annunciators extinguished.



Avionics Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONEFIS Power Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONOverhead Panel Master Panel Lights . . . . . . . .AS REQUIREDEMERGENCY LIGHTS . . . . . . . . . . . . . . . . . . .AS REQUIREDNO SMK FSB Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONAnnunciators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

Press the test button on the glareshield and ensure eachannunciator is illuminated by two lamps.

Fuel Panel CheckFuel Quantity . . . . . . . . . . . . . . . . . . CHECK MAIN/AUX/TESTFuel Firewall Valves . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE

Pressing the ENG FIRE F/W VALVE PUSH CLOSED willclose the shutoff valve and armed the fire extinguisher sys-tem. The firewall valve and extinguisher light switches willilluminate.

Boost Pumps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONFUEL PRESSURE Annunciators . . . . . . . . . ILLUMINATED

Fuel Firewall Valves . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPENFUEL PRESSURE Annunciators . . . . . . . EXTINGUISHED

Boost Pumps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFFUEL PRESSURE Annunciators . . . . . . . . . ILLUMINATED

Crossfeed Switch. . . . . . . . . . . . . . . . . . . . . . ALTERNATE L/RCROSSFEED Annunciator . . . . . . . . . . . ON (each position)FUEL PRESSURE Annunciators . . . . . . . EXTINGUISHED

(each position)Crossfeed Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFAux Fuel Qty . . . . . . . . . . . . . . . . . . .FUEL LOW LEVEL TEST


CAE SimuFlite

Oxygen System CheckOxygen Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

See Normal Procedures section for correct oxygen pressureand duration for the flight.

Oxygen Duration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECKPilot/Copilot Mic Switches . . . . . . . . . . . . . . . .OXYGEN MASKPilot’s Transmitter Switch. . . . . . . . . . . . . . . . . . . . . . . . CABINPilot’s Audio Switch . . . . . . . . . . . . . . . . . . . . . . . . . SPEAKERAudio Emergency Switch. . . . . . . . . . . . . . . . . . . . . . . . NORMPaging Volume. . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIREDCopilot’s Audio Switch . . . . . . . . . . . . . . . . . . . . . . . SPEAKERCopilot’s Transmitter Switch . . . . . . . . . . . . . . . . . . . . . CABINSystem Ready T-Handle . . . . . . . . . . . . . . . . . . . . . . . . . PULLCrew Masks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REMOVEMask Plugs, Mic Plugs. . . . . . . . . . . . . . . . CHECK SECURITYRegulators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK/100%Flowmeters . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK GREENHeadband . . . . . . . . . . . . . . . . . . INFLATE/DEFLATE CHECKMask Microphones. . . . . . . . . . . . . . . . . . . . . . . CHECK EACH

With yoke radio transmitter switch depressed, brief handlingof the mask, or gas release from regulator, should be audi-ble over cabin speaker. Check each side.

Crew Masks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STOWAudio Panel Switches . . . . . . . . . . . . . . . RESET FOR FLIGHTPilot/Copilot Mic Switches . . . . . . . . . . . . . . . . . . . . . NORMAL



Warning System CheckGear Handle Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

Ensure that both handle lamps illuminate. HYD FLUID SENSOR Button . . . . . . . . . . . . . . . PUSH/HOLD

Allow 5 seconds for illumination of HYD FLUID LOWannunciator.

Flap Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ZEROLDG GEAR WARN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

The landing gear warning switch will test the horn and land-ing gear handle lights.

STALL WARN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

Pressing the stall warn test will activate the warning systemand a warning tone should sound. Observe movement of thewing lift transducer.

OVERSPEED WARN. . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

Pressing the overspeed warn test switch will test the systemand a warning tone should sound.

CABIN DIFF WARN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

Observe red CABIN DIFF HI annunciator.CABIN ALT WARN. . . . . . . . . . . . . . . . . . . . . . TEST/SILENCE

Note aural tone, silence button operation, and observe bothCABIN ALTITUDE and CABIN ALT HI annunciators.

ENG FIRE DET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

Placing the ENG FIRE TEST switches into the DET positionwill test the detection circuitry and illuminate the ENG FIREand flashing MASTER WARNING annunciators.

ENG FIRE EXT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST

Selecting the ENG FIRE TEST to EXT position will test thedischarging system and illuminate the corresponding engineEXTINGUISHER PUSH and DISCHARGED annunciators.


CAE SimuFlite

Electric Trim System CheckElectric Trim Switch . . . . . . . . . . . . . . . . . . . . . . . . . RESET/ON

Observe that the ELEC TRIM OFF annunciator is extinguished.Pilot’s Trim Switches . . . . . . . . . . . . ACTIVATE INDIVIDUALLY

Individual activation of the dual-element trim switchesshould cause no trim wheel motion.

Pilot’s Trim Switches . . . . . . . . . . . . . . ACTIVATE TOGETHER

Pressing the dual-element switch on the pilot or copilot con-trol will move the control surfaces to the selected position.

Trim Disconnect Switch . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH

Electric Trim Switch . . . . . . . . . . . . . . . . . . . . . . . . . RESET/ONCopilot’s Trim Switch . . . . . . . . . . . . . . . . . . . . . . . . . . REPEATPilot’s Trim Switches . . . . . . . . . . . . . . . . . . . . . . . . ACTIVATE

Observe pilot’s ability to override copilot’s trim actuationwhen switches are used in opposite directions.

Autopilot and Yaw Damp CheckManual Pitch Trim . . . . . . . . . . . . . . . . . . TAKEOFF POSITIONELEV Trim Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONYaw Damp Button . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE

Note rudder pedals respond to yaw damp engagement.Rudder Boost Switch . . . . . . YAW CONTROL TEST/RELEASE

Observe YD DISC flash momentarily on EFIS ADI, then extinguish.Rudder pedals released.

Rudder Boost/Yaw Control Test Switch . . . . RUDDER BOOSTControl Yoke . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELAX

NOTE: Trim wheel movement stops. ELEV TRIM OFF annunciator illuminates.



Autopilot Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGENote trim wheel movement stops. ELEV TRIM OFF annun-ciator illuminates. AP and YD illuminate steady on EFIS.

Electric Pitch Trim . . . . . . . . . . . . . . . . . . . . . . . . . . .ACTUATEElectric pitch trim switches should be tested in both direc-tions with the autopilot engaged to verify the autopilot dis-connects with all switch activations.Repeat for both pilot and copilot.

Control Yoke . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CENTERAutopilot Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE

Allow green AP and YD annunciators to illuminate steady onEFIS ADI.

Control Yoke . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH/PULLMove the yoke in both the forward and aft directions to verifythe autopilot attempts to trim off the applied pressure.

Turn Knob . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . L/RConfirm that the control wheel responds appropriately tocontrol from the detent position.

Turn Knob . . . . . . . . . . . . . . . . . . . . . . . . . . CENTER DETENTHDG Mode. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGEHDG Control Knob. . . . . . . . . . . . . . . . . . . . . . . . PUSH SYNCHDG Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . L/R

Observe control yoke follows heading commands.Yoke CWS/SYNC button . . . . . . . . . . . . . . . . PUSH/RELEASE

Confirm roll response from previous step becomes inactivewhen button pressed.Repeat previous four steps for both pilot and copilot.

GA Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSHObserve EFIS command bars pitch to +7 degrees.Autopilot disconnects but yaw damp remains engaged.

Autopilot Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE

2A-14 Developed for Training Purposes King Air 350February 2006

CAE SimuFlite

AP/Trim Disconnect . . . . . . . . . . . . . . . . . . . . . PUSH first level

AP DISC and YD DISC flash momentarily on EFIS, thenextinguish.Repeat for both pilot and copilot side.

A/P test button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH

All annunciators illuminate, then extinguish. GA remains illu-minated. Any other annunciator remaining illuminated indi-cates a malfunction.

EFIS test button. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH

Anti-Ice System CheckPitot, Fuel Vent, Stall Warning Heat Switches . . . . . . . . . . . ON

CAUTION: Ensure pitot covers are removed.

Ensure that the optional L or R PITOT HEAT annunciatorextinguishes when switch is selected on.

Pilot/Copilot WindshieldHeat Switches . . . . . . . . . . . . . . . . . CHECK EACH POSITION

Ensure that both windshields are getting heat in low andhigh settings. Observe magnetic compass deflection.

ENGINE ANTI-ICE Actuator Switches. . . . . . . . . . . .STANDBYENGINE ANTI-ICE Switches . . . . . . . . . . . . . . . . . . . . . . . . ON

Observe that the L and R ENG ANTI-ICE annunciators areilluminated.

ENGINE ANTI-ICE Switches . . . . . . . . . . . . . . . . . . . . . . . OFFObserve that the L and R ENG ANTI-ICE annunciators areextinguished.

ENGINE ANTI-ICE Actuator Switches. . . . . . . . . . . . . . . MAINPitot, Fuel Vent, Stall Warning Heat Switches . . . . . . . . . . OFF



Cockpit Preflight ContinuedTrim Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

Trim should be set for takeoff and indicator readings mustmatch trim positions.

External Light Switches . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Functionally check all the lights before flight; see minimumequipment list (MEL) for required lights.

Cockpit Fire Extinguisher. . . . . . . . . . . . . CHECK PRESSUREFlight Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK


CAE SimuFlite

Cabin PreflightForward Cabin Sign . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONFwd Emergency Exit Sign . . . . . . . . . . . . . . . . . . TEST/RESETEmergency Exits . . . . . . . . . . . . . . . . . . . . . . . . . . UNLOCKED

Interior lock must be in the unlock position to permit accessfrom outside the aircraft in case of an emergency.

Coffee Bar . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED

The coffee bar should be in the stowed position (doorclosed) and loose items should be stored.

Cabin Seats, Seat Belts, Shoulder Harnesses . . AS DESIRED

Ensure all seat belt and shoulder harnesses are present andin good condition.

Tray Tables, Cabinets . . . . . . . . . . . STOWED/AS REQUIREDLoose Articles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECUREDCabin Windows . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIREDGasper Vents/Reading Lights . . . . . . . . . . . . . . . AS DESIREDCabin Fire Extinguisher . . . . . . . . . . . . . . CHECK PRESSUREAft Emergency Exit Sign . . . . . . . . . . . . . . . . . . . TEST/RESETAft Cabin Sign . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONFirst Aid Oxygen Mask. . . . . . . . . . . . . . . . . . . . . . . . . .CHECKToilet Knife Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPENDocuments. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECKBaggage Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECUREBaggage Light . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED


CAE SimuFlite

Preflight Inspection Walkaround Path

B3

CR

HP

F0

02

i

A

B

C D

E

G

HI

K

L

N M

F

J



Exterior PreflightGeneralBefore starting the exterior inspection, obtain the following:

flashlight

wiping cloth

standard and Phillips head screwdrivers

step stool

container for fuel sample disposal.All Surfaces . . . . . . . . . . . . . FREE FROM SNOW/ICE/FROSTProtective Covers/Plugs . . . . . . . . . . . . . . . . REMOVE/STOW

Remove safety covers from the engines, static ports andpitot probes.

All Intakes/Exhausts. . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEARFasteners/Panels. . . . . . . . . . . . . . . . . . . . . . . . . ALL SECURE

Verify that all fasteners and panels are secure. Removekeys from locks.

General Condition . . . . . . . . . . . . . . . . . . . . . . . UNDAMAGED

Perform a general condition check of the entire aircraft. Noteany fuel, oil or hydraulic leaks. Determine the cause andhave corrected before flight.

NOTE: If night flight is anticipated, check actual opera-tion of navigation and strobe lights.


CAE SimuFlite

A Left Wing Trailing EdgeLeft Side Cabin Windows. . . . . . . . . . . . . . . . . . . . . . . .CHECKFlap Symmetry. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

The inboard flap should lay flush with the bottom of the fuse-lage fillet. Lateral movement of any flap panel is unacceptable.Do not exceed one flap travel every 10 minutes on theground.Both flap panels should be fully retracted. Ensure they arenot bent or distorted. Some movement of the flaps should bepossible, and there should be no sign of flap binding. Noteespecially the condition of rivets on top of the flaps. Theinboard flap must be flush with the bottom of the fuselage;the outboard flap trailing edge may vary from 1/4-inch aboveto 1/4-inch below the inboard flap.

Landing Gear and Doors:

Ensure tires are in good condition, doors are secure, strutsare properly inflated, and wheel wells are clean and free offluid leaks. Linkage should be secure with no signs ofunusual wear or cracking. Check uplock and downlockmicroswitches for condition. Brake deice lines, wheninstalled, should be secure and free of fuel, oil, and hydrau-lic fluid. The deice manifold should be securely attached tothe axle and free of damage. Brake lines should be secureand free of fraying or leaking.

Tire Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECKStrut Inflation/Cleanliness . . . . . . . . . . . . . . . . . . . . . . .CHECKAll Linkages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK



Brakes, Lines & Plumbing . . . . . . . . . . . . . . . . . . . . . . .CHECK

Table 2A; Main Gear ConditionsFire Extinguisher Pressure . . . . . . . . . . . . . . . . . . . . . .CHECK

Check that the fire extinguisher cylinder is properly serviced.The cylinder is located aft in the main wheel well. Refer toTable below for fire extinguisher cylinder pressure.

Table 2-B; Fire Extinguisher Cylinder PressureOil Breather Vent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

Main Gear Condition

Aircraft Loading Tire Inflation(PSI)

Strut Extension(Inches)1

Unloaded 83-87 3.23-3.49

Loaded 88-92 3.23-3.491 Strut extension is with full fuel and oil.

Fire Extinguisher Cylinder

Ambient Temperature Indicated Pressure (PSI)

ºF ºC-40 -40 190-240-20 -29 220-2750 -18 250-315

20 -7 290-36540 4 340-42060 16 390-48080 27 455-550100 38 525-635120 49 605-760


CAE SimuFlite

Fuel Sump (outboard of wheel nacelle) . . . . . . . . . . . . . DRAIN

Six fuel sumps must be drained on each wing. Two sumpsare quick-drain style and four are flush-mounted. Use a fueltester probe to push up on the spring-loaded push-to-draintype valve. Check for water and/or sediment. Dispose ofsamples in a fuel sample container. At this point, check thegravity feed line from wing tanks to nacelle (aft of wheelwell).

Inverter Louvers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEARHeated/NACA Fuel Vents . . . . . . . . . . . . . . . . . CLEAR/WARMAileron, Tab, Static Wicks (5) . . . . . . . . . . . . CHECK/NEUTRAL

The aileron and the trim tab should be in the neutral posi-tion, as previously set in the cockpit. The aileron can be asmuch as 1/2-inch above or below the flap trailing edge.Check general condition and freedom of movement of theaileron. Check bonding wires for secure attachment. Thetrim tab should be aligned with the aileron. The hinge shouldnot have excess play.Check for three static wicks on the left aileron and two staticwicks on the winglet.

Bonding Cables (1 each hinge) . . . . . . . . . . . . . . . . . . .CHECKOutboard Fuel Vents . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

LimitationsAll wicks must be installed in good condition when using VLF equipment.

NOTE: One wick may be damaged or missing on any one surface.



B Left Wing Leading EdgeWing Tip Light Group . . . . . . . . . . . . . . CHECK (NO CRACKS)

Check the light assembly for lens cracks, security, and anyindication of a burned out bulb.

Main Tank Cap. . . . . . . . . . . . . . CHECK/SECURE/NO LEAKS

Ensure there are no leaks in the main fuel tank. Check thefuel cap near the wing tip; the locking tab should be flushwith the surface of the cap and pointing aft.

Stall Warning Vane. . . . . . . . . . . . . CHECK FREEDOM/WARM

Check that the stall warning vane on the leading edge of theleft outboard wing section moves freely and that the vaneand mounting assembly are in good condition.

Flush Drain . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DRAINDeice Boot/Stall Strip . . . . . . . . . . . . . . . . . . .CHECK/SECURE

The deice boot should be securely attached to the leadingedge. Ensure that it is undamaged. Check for significantscratches or cuts in the boot. Check condition of the stallstrip attached to the boot.

Access Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECUREMain Tank Fuel Sumps . . . . . . . . . . . . . . . . . . . . . . . . . DRAIN

Drain the flush-mounted nacelle fuel pump, strainer, and fuelfilter drains forward of the wheel well. Check condition ofsamples.

Ice Inspection Light . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Check ice inspection light for condition and security.


CAE SimuFlite

C Left Engine NacelleFirewall Sump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DRAINNacelle and Strainer Sump . . . . . . . . . . . . . . . . . . . . . . DRAINEngine Oil Breather Vent . . . . . . . . . . . . . . . . . . . . . . . . CLEAROil Cooler and Ice Vane Exhaust. . . . . . . . . . . . . . . . . . CLEAREngine Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECKLeft Engine Cowling:

Linkages, Lines, Hoses,Accessories. . . . . . . . . . . .CHECK SECURITY/CONDITIONBonding Straps,Cable Ties . . . . . . . . . . . . .CHECK SECURITY/CONDITIONOil Dipstick . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

Cowling . . . . . . . . . . . . . . . . . CAMLOCS/LATCHES/SCREWSExhaust Stacks and Scuppers . . . . . . . . . . . . . . . . . . . .CHECKForward Cowl Air Intakes. . . . . . . . . . . . . . . . . . . . . . . . CLEARPropeller . . . . . . . . . . . . . . . . .CHECK SECURITY/LEAKAGE/

NICKS/BOOTSEngine Intake. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAROil Cooler Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

Ice Vane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACTEDRight Engine Cowling:

Linkages, Lines, Hoses,Accessories. . . . . . . . . . . .CHECK SECURITY/CONDITIONBonding Straps,Cable Ties . . . . . . . . . . . . .CHECK SECURITY/CONDITIONGenerator Blast Tube . . . . . . . . . . . . . . . . . . . . . . . .CHECKSwing Check Valve Louver . . . . . . . . . . . . . . . . . . . . CLEARNo obvious evidence of fluid leaks, heat damage, chafing,loose hardware, or rubbing on interior of cowl covers, etc.

Cowling . . . . . . . . . . . . . . . . . CAMLOCS/LATCHES/SCREWS



D Left Wing RootAux Tank Cap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

Inspect the wing in the area of the auxiliary fuel tank, andensure the fuel cap is secure and locked with the tab point-ing aft. Ensure the hydraulic gear service door is secure andthat the hydraulic gear overfill and vent lines are clear.

Hydraulic Powerpack Service Door . . . . . . . . . . . . . . SECUREInboard Deice Boot . . . . . . . . . . . . . . . . . CHECK CONDITION

The deice boot should be securely attached to the leadingedge. Check for significant scratches or cuts in the boot.

Heat Exchanger Inlet and Exhaust . . . . . . . . . . . . . . . . CLEAR

Check the heat exchanger inlet and outlet for cracks orobstructions.

Hydraulic Gear Powerpack Vents . . . . . . . . . . . . . . . . . CLEAR

Make sure that the vents are not dented, damaged orleaking.

Aux Fuel Drain . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DRAINAccess Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURELower Antennas. . . . . . . . . . . . . . . . . SECURE/UNDAMAGED

Check the underside of the aircraft for signs of fuel or otherleaks. Check antennas, beacon and panels for security andcondition.


CAE SimuFlite

E Left NoseEmergency Exit . . . . . . . . . . . . . . . . . . . . . . . FLUSH/SECURETemperature Probe . . . . . . . .CHECK SECURITY/CONDITION

Ensure that the security and condition of the temperatureprobe on the lower fuselage is satisfactory.

Relief Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECKBrake Reservoir Vent. . . . . . . . . . . . . . . . . . . . . . . . . . . CLEARWindshield and Wiper . . . . . . CONDITION/SECURE/PARKED

The windshield should be clean, free from cracks, discolora-tion, and excessive delamination. Ensure security and con-dition of the pilot wiper arm assembly.

Avionics Door. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURECondenser Blower . . . . . . . . . . . . . . . . . CLEAR/UNDAMAGEDPitot Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR/WARM

Ensure the pitot cover is removed and that the pitot tube issecure and in good condition.



F Nose GearRadome . . . . . . . . . . . . . . . . . . . . . . . . CHECK/UNDAMAGED

Radome should be clean and free of cracks. Verify that theradome is properly secure.

Landing/Taxi Lights . . . . . . . . . . . . . . . . . . . .CHECK/SECURE

Check condition and security of the landing and taxi lights.Ensure chocks are removed. Verify functionality of all lights.

Nose Strut . . . . . . . . . . . . . . . . . . . . . . . . CHECK CONDITION

Table 2A-A; Nose Gear Conditions

Shimmy Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURETurn Limit Stop. . . . . . . . . . . . . . . . . . . . CLEAN/UNDAMAGED

Metal plate should be straight and holes should be circular. Gear Doors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

Check that the nose gear door hinges are in good condition.Ensure turn limits on the nosewheel strut have not beenexceeded. Check condition of the uplock and downlockmicroswitches. Check tire, wheels, strut linkages and doors.

Air Conditioning Reset CB . . . . . . . . . . . . . . . . . . .UNTRIPPEDWheel Well Access Panels . . . . . . . . . . . . . . . . . . . . SECURE

Nose Gear Condition

Tire Inflation(PSI)

Strut Extension(inches)1

55-60 3.77-4.061 Strut extension is with full fuel and oil.


CAE SimuFlite

G Right NosePitot Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR/WARM

Ensure the pitot cover is removed and that the pitot tube issecure and in good condition.

Condenser Inlet . . . . . . . . . . . . . . . . . . . . . . . CLEAR/SECURE

Check that the inlet duct is free of obstructions.Avionics Door. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

Check that the right access panel and all fasteners aresecurely attached.

Windshield and Wiper . . . . . . CONDITION/SECURE/PARKED

The windshield should be clean, free from cracks, discolora-tion, and excessive delamination. Ensure security and con-dition of the pilot wiper arm assembly

CAUTION: Do not operate the windshield wiper on adry windshield; damage to wiper and windshield canoccur.



H Right Wing RootEmergency Exit . . . . . . . . . . . . . . . . . . . . . . . FLUSH/SECUREAux Tank Cap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

Ensure there are no leaks. Check the fuel cap; the lockingtab should be flush with the surface of the cap and pointingaft.

Inboard Deice Boot . . . . . . . . . . . . . . . . . CHECK CONDITION

The deice boot should be securely attached to the leadingedge. Check for significant scratches or cuts in the boot.

Heat Exchanger Inlet and Exhaust . . . . . . . . . . . . . . . . CLEAR

Check the heat exchanger inlet and outlet for cracks orobstructions. Ensure ejector exhaust is clear of anyobstructions.

Vacuum Ejector Exhaust . . . . . . . . . . . . . . . . . . . . . . . . CLEARAux Fuel Tank Drain . . . . . . . . . . . . . . . . . . . . . . . . . . . DRAIN

Six fuel sumps need to be drained on each wing. Twosumps are quick-drain style and four are flush-mounted.Use a fuel tester probe to push up on the spring-loadedpush-to-drain type valve. Check for water and/or sediment.Dispose of samples in a fuel sample container. At this point,check the inboard fuel tank sump on the underside of theauxiliary tank near the fuselage.

Battery Box Drain. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEARBattery Air Inlet and Exhaust . . . . . . . . . . . . . . . . . . . . . CLEAR

The battery air inlet is on the bottom of the wing between thenacelle and the fuselage. The thermostatically controlledvalve should be securely in place, should not bind, andshould be in the proper position for battery box temperature(fully open at 70 to 80°F and fully closed at 30°F).Ensure that the battery outlet vent on top of the wing isunobstructed and the access panel is secure. Check thebattery box drain for obstructions.

Lower Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE


CAE SimuFlite

I Right Engine NacelleFirewall Sump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DRAINNacelle and Strainer Sump . . . . . . . . . . . . . . . . . . . . . . DRAINEngine Oil Breather Vent . . . . . . . . . . . . . . . . . . . . . . . . CLEAROil Cooler and Ice Vane Exhaust. . . . . . . . . . . . . . . . . . CLEAREngine Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Left Engine Cowling:

Linkages, Lines, Hoses,Accessories. . . . . . . . . . . .CHECK SECURITY/CONDITION

Bonding Straps,Cable Ties . . . . . . . . . . . . .CHECK SECURITY/CONDITION

Oil Dipstick . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

AC Compressor Drive Belt . . . . . . . . . . . . . . . . . . SECURECowling . . . . . . . . . . . . . . . . . CAMLOCS/LATCHES/SCREWSExhaust Stacks and Scuppers . . . . . . . . . . . . . . . . . . . .CHECKForward Cowl Air Intakes. . . . . . . . . . . . . . . . . . . . . . . . CLEARPropeller . . . . . . . . . . . . . . . . .CHECK SECURITY/LEAKAGE/

NICKS/BOOTSEngine Intake. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAROil Cooler Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

Ice Vane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACTED

Right Engine Cowling:

Linkages, Lines, Hoses,Accessories. . . . . . . . . . . .CHECK SECURITY/CONDITION

Bonding Straps,Cable Ties . . . . . . . . . . . . .CHECK SECURITY/CONDITION

Generator Blast Tube . . . . . . . . . . . . . . . . . . . . . . . .CHECK



Swing Check Valve Louver . . . . . . . . . . . . . . . . . . . . CLEAR

No obvious evidence of fluid leaks, heat damage, chafing,loose hardware, or rubbing on interior of cowl covers, etc.

Cowling . . . . . . . . . . . . . . . . . CAMLOCS/LATCHES/SCREWS


CAE SimuFlite

J Right Wing Leading EdgeLanding Gear and Doors:

Ensure tires are in good condition, doors are secure, strutsare properly inflated, and wheel wells are clean and free offluid leaks. Linkage should be secure with no signs ofunusual wear or cracking. Check uplock and downlockmicroswitches for condition. Brake deice lines, wheninstalled, should be secure and free of fuel, oil, and hydrau-lic fluid. The deice manifold should be securely attached tothe axle and free of damage. Brake lines should be secureand free of fraying or leaking.Tire Pressure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Strut Inflation/Cleanliness . . . . . . . . . . . . . . . . . . . . .CHECK

Check for evidence of leaks and friction, general condi-tion and proper installation (refer to Table 2-A).

All Linkages. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Check for wear and evidence of friction; all linkagesshould have free movement.

Brakes Lines and Plumbing . . . . . . . . . . . . . . . . . . .CHECK

Fire Extinguisher Pressure . . . . . . . . . . . . . . . . . . . .CHECK

Check that the fire extinguisher cylinder is properly ser-viced (refer to Table 2-B). The cylinder is located aft inthe main wheel well.

GPU Access Door. . . . . . . . . . . . . . . . . . CLOSED (IF GPU DISCONNECTED)

Confirm that the door is closed, undamaged and properlylatched. If GPU is still connected to the aircraft, ensure thatthe door is properly closed after removal.

Inverter Louvers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEARNacelle and Strainer Sump . . . . . . . . . . . . . . . . . . . . . . DRAIN



Firewall Sump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DRAIN

Drain the flush-mounted firewall fuel filter drain; it is flushwith the bottom of the firewall. Check condition of sample.

Ice Inspection Light . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Check ice inspection light for condition, security andoperation.

Main Tank Fuel Sumps . . . . . . . . . . . . . . . . . . . . . . . . . DRAINHeated/NACA Fuel Vents . . . . . . . . . . . . . . . . . CLEAR/WARMDeice Boot/Stall Strip . . . . . . . . . . . . . . . . . . .CHECK/SECURE

The deice boot should be securely attached to the leadingedge. Ensure that it is undamaged. Check for significantscratches or cuts in the boot. Check condition of the stallstrip attached to the boot.

Access Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECUREMain Tank, Cap . . . . . . . . . . . . . CHECK/SECURE/NO LEAKS

Ensure there are no leaks in the main fuel tank. Check thefuel cap near the wing tip; the locking tab should be flushwith the surface of the cap and pointing aft.

Outboard Fuel Vents . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

Check the general condition of the siphon break vent on theaft side of the wing tip. It should be clear and free ofobstructions.

Wing Tip Light Group . . . . . . . . . . . . . . CHECK (NO CRACKS)

Check the light assembly for lens cracks, security, and anyindication of a burned out bulb.


CAE SimuFlite

K Right Wing Trailing EdgeAileron, Tab, Static Wicks (5) . . . . . . . . . . . . CHECK/NEUTRAL

The aileron and the trim tab should be in the neutral posi-tion, as previously set in the cockpit. The aileron can be asmuch as 1/2-inch above or below the flap trailing edge.Check general condition and freedom of movement of theaileron. Check bonding wires for secure attachment. Thetrim tab should be aligned with the aileron. The hinge shouldnot have excess play.Check for three static wicks on the left aileron and two staticwicks on the winglet.

Bonding Cables (1 each hinge) . . . . . . . . . . . . . . . . . . .CHECKFuel Sump (outboard of wheel nacelle) . . . . . . . . . . . . . DRAIN

Drain the gravity feed line from wing tanks to nacelle (aft ofwheel well).

Flap Symmetry. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

The inboard flap should lay flush with the bottom of the fuse-lage fillet. Lateral movement of any flap panel isunacceptable.Do not exceed one flap travel every 10 minutes on theground.Both flap panels should be fully retracted. Ensure they arenot bent or distorted. Some movement of the flaps should bepossible, and there should be no sign of flap binding. Noteespecially the condition of rivets on top of the flaps. Theinboard flap must be flush with the bottom of the fuselage;the outboard flap trailing edge may vary from 1/4-inch aboveto 1/4-inch below the inboard flap.




L Right Rear FuselageRight Side Cabin Windows . . . . . . . . . . . . . . . . . . . . . .CHECK

Do a visual inspection of the windows, ensure they areclean, properly installed and free of any cracks.

Oxygen Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

Verify that the door is secure, latches are not loose and dooris undamaged.

Static Ports. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

Ensure that the ports are clean and no evidence of corrosionexists.

Tailcone Access Panels . . . . . . . . . . . . . . . . . . . . . . . SECURE

Ensure that the tailcone access door and inspection panelsare secure.

ELT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARMED

The emergency locator transmitter (ELT) is aft of the oxygendoor and static ports on the fuselage. Push the door in andensure the switch is in the ARMED/AUTO position. Checkthe ELT antenna for condition and security.

All Antennas. . . . . . . . . . . . . . . . . . . . . CHECK/UNDAMAGED

Check the underside of the aircraft for leaks. Check anten-nas and beacon for security and condition. Ensure aft relieftube drain is unobstructed. Check the aft compartment bot-tom access panels for condition and security.


CAE SimuFlite

M EmpennageVentral Fin Drain Holes . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

Ensure the ventral fin water drain is unobstructed.Control Surfaces/Tabs . . . . . . . . . . . . . . . .SECURE/NEUTRAL

Ensure trim tabs are in line with control surfaces. Checkdrain holes on underside of elevator. Verify all trim tabs arein the neutral position. The elevator trim tab neutral position(previously set in the cockpit) can be checked by observingthat the trailing edge of the trim tab aligns with the trailingedge of the elevator when the elevator is resting against thedownstops.

Static Wicks (13) . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

Check for four static wicks on each elevator, four static wickson the rudder, and one static wick on the vertical stabilizer.

Bonding Cables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

The cables should be properly installed and undamaged.Exterior Light Groups. . . . . . . . . . . . . . . CLEAN/UNDAMAGED

Visually inspect the navigation lights, strobe lights andfloodlights.

Surface Deice Boots . . . . . . . . . . . . . . . CLEAN/UNDAMAGED

The deice boots should be secure and in good condition.Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Check the VOR antennas for condition and security.


LimitationsAll wicks must be installed in good condition when using VLF equipment.



N Left Rear FuselageAccess Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

Ensure all access panels are secure.Static Ports. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR

Check static ports for condition.Oxygen Overpressure Discharge Vent . . . . . . . . . . . . . CLEARRelief Tube. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK

Ensure that the relief tube is clear and undamaged.Cabin Door

Circuitry Check . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE

Door Seal . . . . . . . . . . . . . . . . . . . . .CLEAN/UNDAMAGED

Latching Bayonets. . . . . . . . . . . . . . . . CHECK CONDITION

Piano Hinge/Rivets/Snubber . . . . . . . . CHECK CONDITION

Steps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FIRM

Cable, Air Supply, Wiring . . . . . . . . . . . . . . . . . . . . .CHECK


CAE SimuFlite